The invention discloses an adjustable active thermal protection system for a hypersonic aircraft. The system comprises an air guide pipe; one end of the air guide pipe is open, the other end of the air guide pipe is closed, the open end is rotationally connected with an aircraft nose cone at a through hole in the axis of the aircraft nose cone, a locking mechanism is arranged at the joint, and a plurality of nozzles are circumferentially and evenly formed in the side wall of the closed end. When the protection system works, the air guide pipe leads low-temperature air out of a high-pressure tank in an aircraft cabin and then sprays the low-temperature air out of a nozzle in the side wall to form lateral jet flow, so that incoming flow with the compressed flow speed reduced through the closed end of the air guide pipe is reduced again, the aerodynamic heating effect of the aircraft nose cone is weakened, and the heat flux of the wall surface of the nose cone is reduced; and meanwhile, the sprayed low-temperature air flows downstream along with the main flow to perform film cooling on the wall surface of the nose cone. The defect that a traditional active thermal protection system islow in thermal protection efficiency in a non-zero attack angle state can be overcome, and lateral jet flow has lower critical total pressure than traditional reverse jet flow and is easier to implement.
本发明公开了一种可调式高超声速飞行器主动热防护系统,包括引气管;引气管为一端开口一端封闭,开口端在飞行器头锥轴线的通孔处和飞行器头锥转动连接,且连接处设有锁止机构,封闭端的侧壁上周向均匀设有若干喷口。工作时,引气管从飞行器舱体内的高压罐中引出低温空气后从侧壁上的喷口喷出,形成侧向喷流,使得经过引气管封闭端压缩流速降低后的来流再次降低流速,减弱飞行器头锥的气动加热效应,减小头锥壁面热流密度,同时喷出的低温空气随主流往下游流动,对头锥壁面进行膜冷却。本发明能够解决传统主动热防护系统在非零攻角状态下防热效率低的缺点,且侧向喷流比传统逆向喷流具有更低的临界总压,更易于实现。
Adjustable active thermal protection system for hypersonic aircraft
一种可调式高超声速飞行器主动热防护系统
2021-03-16
Patent
Elektronische Ressource
Chinesisch
IPC: | B64C AEROPLANES , Flugzeuge |
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